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Volume 24 Issue 2
Feb.  1998
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Journal of Beijing University of Aeronautics and Astronautics  > 1998  >  24(2): 233-236.
Zhang Zhengke, Zhu Ziqiang, Zhuang Fengganet al. Numerical Simulation of Vortical Flows over Fighter Configuration with Euler Equations[J]. Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(2): 233-236. (in Chinese)
Citation: Zhang Zhengke, Zhu Ziqiang, Zhuang Fengganet al. Numerical Simulation of Vortical Flows over Fighter Configuration with Euler Equations[J]. Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(2): 233-236. (in Chinese)
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Numerical Simulation of Vortical Flows over Fighter Configuration with Euler Equations

  • 1.

    Beijing University of Aeronautics and Astronautics, School of Astronautics

  • 2.

    Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Design and Applied Mechanics

  • Received Date: 02 Sep 1996
  • Publish Date: 28 Feb 1998
    Abstract
  • A three-stage explicit scheme is used for time-stepping solutions of Euler equations discretized in physical curvilinear grid cell of finite volume simulating vortical flows over a generic fighter configuration. The predicted pressure distribution on wing surface is in good agreement with experiments. The primary vortex from leading edge of wing as well as the secondary vortex on upper wing surface is captured. The secondary vortex in the solution of Euler equations is attributed to the combined effect of adverse pressure gradient, sharp edge and artificial viscosity, and the flow picture of the secondary vortex is qualitatively similar to that of experimental observation.

     

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    • References(1)
  • 1.Berg J I van den,Hoeijmakers H W M,Brandsma F J.Numerical investigation into vortical flow about a deltawing configuration up to incidences at which vortex breakdown occurs in experiment.AIAA 94-0621,1994 2. 张正科.多部件复杂飞行器分块网格生成及其大迎角绕流场Euler方程分区解.博士后研究工作报告,北京航空航天大学飞行器设计与应用力学系,1996 3. 张正科. 翼身组合体跨音速大迎角欧拉方程多重网格数值解:[学位论文]. 西安:西北工业大学飞机系,1994 4. 蔡晋生,罗时钧. 贴体与边界正交网格及大迎角涡流计算. 空气动力学学报,1993,11(4):451~455 5. Runckel J F,Lee Jr E E.Investigation at transonic speeds of the loading over a 45° sweptback wing having an aspect ratio of 3,a taper ratio of 0.2,and NACA 65A004 airfoil sections.NASA TND-712,1961
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